[Federal Register Volume 69, Number 183 (Wednesday, September 22, 2004)]
[Rules and Regulations]
[Pages 56687-56688]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-21270]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-54-AD; Amendment 39-13802; AD 2004-19-08]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Rolls-Royce plc (RR) RB211 Trent 800 series turbofan engines. This AD 
requires revising the Time Limits Manual for RR RB211 Trent 800 series 
turbofan engines. These revisions include required enhanced inspection 
of selected critical life-limited parts at each piece-part exposure. 
This AD results from the need to require enhanced inspection of 
selected critical life-limited parts of RB211 Trent 800 series turbofan 
engines. We are issuing this AD to prevent failure of critical life-
limited rotating engine parts, which could result in an uncontained 
engine failure and damage to the airplane.

DATES: This AD becomes effective October 27, 2004.

ADDRESSES: You can get the service information identified in this AD 
from Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; 
telephone: 011-44-1332-242424; fax: 011-44-1332-249936.
    You may examine the AD docket at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (781) 238-7175, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to RR RB211 Trent 800 
series turbofan engines. We published the proposed AD in the Federal 
Register on March 4, 2004 (69 FR 10179). That action proposed to 
require revising the Time Limits Manual for RR RB211 Trent 800 series 
turbofan engines to include required enhanced inspection of selected 
critical life-limited parts at each piece-part exposure.

Examining the AD Docket

    You may examine the AD Docket (including any comments and service 
information), by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. See ADDRESSES for the 
location.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the proposal or on 
the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    There are about 350 engines of the affected design in the worldwide 
fleet. We estimate that 90 engines installed on airplanes of U.S. 
registry are affected by this AD. We also estimate that it will take 
about 75 work hours per engine to perform the inspections, and that the 
average labor rate is $65 per work hour. Since this is an added 
inspection requirement, included as part of the normal maintenance 
cycle, no additional part costs are involved. Based on these figures, 
the total cost impact of the AD on U.S. operators is estimated to be 
$438,750.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2003-NE-54-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2004-19-08 Rolls-Royce plc: Amendment 39-13802. Docket No. 2003-NE-
54-AD.

Effective Date

    (a) This AD becomes effective October 27, 2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 800 
series turbofan engines. These engines are installed on, but not 
limited to, Boeing 777 airplanes.

Unsafe Condition

    (d) This AD results from the need to require enhanced inspection 
of selected critical life-limited parts of RB211 Trent 800 series 
turbofan engines. The actions specified in this AD are intended to 
prevent critical life-limited rotating engine part failure, which 
could result in an uncontained engine failure and damage to the 
airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.
    (f) Within the next 40 days after the effective date of this AD, 
revise the Time

[[Page 56688]]

Limits Manual (TLM), and for air carrier operations revise the 
approved continuous airworthiness maintenance program, by adding the 
following:

``GROUP A PARTS MANDATORY INSPECTION

    (1) Inspections referred to as `Focus Inspect' in the applicable 
Engine Manual inspection Task are mandatory inspections for the 
components given below, when the conditions that follow are 
satisfied:
    (i) When the component has been completely disassembled to 
piece-part level as given in the applicable disassembly procedures 
contained in the Engine Manual; and
    (ii) The part has more than 100 recorded flight cycles in 
operation since the last piece-part inspection. or
    (iii) The component removal was for damage or a cause directly 
related to its removal; or
    (iv) Where serviceable used components, for which the inspection 
history is not fully known, are to be used again.
    (2) The list of Group A Parts is specified below:

----------------------------------------------------------------------------------------------------------------
                                                                                          Inspected per overhaul
               Part nomenclature                               Part number                     manual task
----------------------------------------------------------------------------------------------------------------
Low Pressure Compressor Rotor Disc.............  All...................................         72-31-16-200-801
Low Pressure Compressor Rotor Shaft............  All...................................         72-31-20-200-801
Intermediate Pressure Compressor Rotor Shaft...  All...................................         72-32-31-200-801
Intermediate Pressure Rear Shaft...............  All...................................         72-33-21-200-801
High Pressure Compressor Stage 1 to 4 Rotor      All...................................         72-41-31-200-801
 Discs Shaft.
High Pressure Compressor Stage 5 & 6 Discs and   All...................................         72-41-31-200-802
 Cone.
High Pressure Turbine Rotor Disc...............  All...................................         72-41-51-200-801
Intermediate Pressure Turbine Rotor Disc.......  All...................................         72-51-31-200-801
Intermediate Pressure Turbine Rotor Shaft......  All...................................         72-51-33-200-801
Low Pressure Turbine Stage 1 Rotor Disc........  All...................................         72-52-31-200-801
Low Pressure Turbine Stage 2 Rotor Disc........  All...................................         72-52-31-200-802
Low Pressure Turbine Stage 3 Rotor Disc........  All...................................         72-52-31-200-803
Low Pressure Turbine Stage 4 Rotor Disc........  All...................................         72-52-31-200-804
Low Pressure Turbine Stage 5 Rotor Disc........  All...................................         72-52-31-200-805
Low Pressure Turbine Rotor Shaft...............  All...................................       72-52-33-200-801''
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Alternative Methods of Compliance

    (g) You must perform these mandatory inspections using the TLM 
and the applicable Engine Manual unless you receive approval to use 
an alternative method of compliance under paragraph (h) of this AD. 
Section 43.16 of the Federal Aviation Regulations (14 CFR 43.16) may 
not be used to approve alternative methods of compliance or 
adjustments to the times in which these inspections must be 
performed.
    (h) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Maintaining Records of the Mandatory Inspections

    (i) You have met the requirements of this AD by using a TLM 
changed as specified in paragraph (f) of this AD, and, for air 
carriers operating under part 121 of the Federal Aviation 
Regulations (14 CFR part 121), by modifying your continuous 
airworthiness maintenance plan to reflect those changes. You must 
maintain records of the mandatory inspections that result from those 
changes to the TLM according to the regulations governing your 
operation. You do not need to record each piece-part inspection as 
compliance to this AD. For air carriers operating under part 121, 
you may use either the system established to comply with section 
121.369 or use an alternative system that your principal maintenance 
inspector has accepted if that alternative system:
    (1) Includes a method for preserving and retrieving the records 
of the inspections resulting from this AD; and
    (2) Meets the requirements of section 121.369(c); and
    (3) Maintains the records either indefinitely or until the work 
is repeated.
    (j) These record keeping requirements apply only to the records 
used to document the mandatory inspections required as a result of 
revising the Time Limits Manual as specified in paragraph (f) of 
this AD, and do not alter or amend the record keeping requirements 
for any other AD or regulatory requirement.

Material Incorporated by Reference

    (k) None.

Related Information

    (l) Civil Aviation Authority (CAA) airworthiness directive No. 
G-2003-0003, dated November 25, 2003, also addresses the subject of 
this AD.

    Issued in Burlington, Massachusetts, on September 15, 2004.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 04-21270 Filed 9-21-04; 8:45 am]
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